Fischer William C. (Monroe CT) Adams Don L. (Fairfield CT) Verzella David J. (Guilford CT) Wright Stuart C. (Milford CT)
출원인 / 주소
United Technologies Corporation (Hartford CT 02)
인용정보
피인용 횟수 :
5인용 특허 :
6
초록▼
In an aircraft automatic flight control system, proportional commands (54, 55) provided to fast, limited authority inner loop actuators (12, 13) are integrated (41), and when the integrator output indicates that the inner loop actuators 12, 13 have been driven a certain percentage of their authority
In an aircraft automatic flight control system, proportional commands (54, 55) provided to fast, limited authority inner loop actuators (12, 13) are integrated (41), and when the integrator output indicates that the inner loop actuators 12, 13 have been driven a certain percentage of their authority, a comparator (130, 132) activates a pulse generator (137, 138) to provide timed excitation of an actuator (150), thereby to position the aircraft control system outer loop by a commensurate increment. Driving the actuator for a longer time than the desired pulse width is detected (165-169) and causes automatic shutdown (190) of the actuator. Resetting the integrator at the start of each pulse (162, 104), and pulse-controlled gating of the pulse circuits (172, 135, 136) allow sensing of authority transitions which occur within a pulse, and permit a subsequent pulse in response thereto.
대표청구항▼
A system for automatically positioning aerodynamic surfaces in a control axis of an aircraft, comprising: a sensor responsive to a parameter of aircraft flight related to said control axis for providing a parameter signal indicative of the magnitude thereof; a fast, inner loop actuator for changing
A system for automatically positioning aerodynamic surfaces in a control axis of an aircraft, comprising: a sensor responsive to a parameter of aircraft flight related to said control axis for providing a parameter signal indicative of the magnitude thereof; a fast, inner loop actuator for changing the position of said aerodynamic surfaces across a limited authority range of positions which is a fraction of the total permissible range of positions thereof; an outer loop actuator connected to said inner loop actuator for adjusting the position of said inner loop actuator relative to the position of said control surfaces throughout a full authority range of positions equal to the total permissible range of positions thereof, to thereby reposition the center of said limited authority range relative to said full authority range; and signal processing means for providing a reference signal indicative of a desired magnitude of said parameter, and responsive to said sensor, for providing a proportional command signal of a first sense indicative of the magnitude and sense of the difference between said parameter signal and said reference signal to adjust the position of said inner loop actuator and therefore of said control surfaces in a first direction, depending on the sense of said difference to cause said parameter signal to approach equally with said reference signal, for providing to said inner loop actuator, a rate command signal indicative of the magnitude and sense of the rate of change of said parameter signal to adjust the position of said control surfaces in a second direction, depending on the sense of said rate of change, to cause the rate of change of said parameter signal to approach nil, and for providing said proportional command signal to said inner loop actuator; characterized by said signal processing means comprising means for providing an integral signal representing an integral function of said proportional command signal, for providing an excess signal indicative of said integral signal exceeding a predetermined magnitude, for providing, in response to said excess signal, a reset signal and an outer loop command signal of a fixed magnitude and predetermined duration and of said first sense to said outer loop actuator, and for resetting said integral function to nil in response to said reset signal.
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이 특허에 인용된 특허 (6)
Murphy Richard D. (Monroe CT) Cotton Lou S. (Monroe CT), Automatic approach to hover system.
Gerstine Milton I. (Wilmington DE) Goldberg Joshua I. (Ridgefield CT) Futatsugi Setsuo (Kagamigahara JA) Ueda Kazuo (Kagamigahara JA) Seo Ryozo (Kagamigahara JA) Iwasaki Koji (Kagamigahara JA) Uemura, Automatic flight control means for rotary wing aircraft.
Adams Don L. (Fairfield CT) Murphy Richard D. (Monroe CT) Fischer William C. (Monroe CT), Desensitizing helicopter control response to inadvertent pilot inputs.
Tefft Franklin A. (Killingworth CT) Perez Ricardo L. (Plantsville CT) Barnum Ronald E. (Trumbull CT), Helicopter hover stability and cruise gust effect alleviation.
Fischer William C. (Monroe CT) Wright Stuart C. (Milford CT) Verzella David J. (Guilford CT), Outer-loop monitor for aircraft automatic flight control system.
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